United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Mani Sadeghi

Daniel L Gysling

Bruce L Morin

Edward J Gallagher

Darryl Whitlow

Sue-Li Chuang

Brian F Hilbert

William D Owen

Scott C Billings

Ian T Marchaj

Michael K Gottschalk

Kerwin R Low

An assembly is provided for rotational equipment. This assembly includes a stationary structure, a rotating structure rotatable about an axial centerline, and a non-contact seal assembly. The non-contact seal assembly is configured to substantially seal a gap between the stationary structure and the rotating structure. The non-contact seal assembly includes a seal shoe configured to sealingly engage the rotating structure axially along the axial centerline.

Non-contact seal with axial engagement

Disclosed is a flutter damper, including an acoustic liner having a perforated radial inner face sheet and a radial outer back sheet, the acoustic liner being configured for peak acoustical energy absorption at a frequency range that is greater than a frequency range associated with fan flutter, a chamber secured to the radial outer back sheet, the chamber being in fluid communication with the acoustic liner, and the chamber being configured for peak acoustical energy absorption at a frequency range that is associated with one or more fan flutter modes, and at least one stiffening structure connected to a top surface of the chamber that tunes the top surface out of the frequency range associated with one or more fan flutter modes.

Flutter dampening acoustic liner for a turbofan engine

Disclosed is flutter damper including a first cavity having a radially inner side in fluid communication with a flow path, and a second cavity having a radially inner side in fluid communication with a radially outer side of the first cavity, and the flutter damper having an impedance characteristic at one or more target frequencies defined as

Flutter inhibiting intake for gas turbine propulsion system

In one exemplary embodiment, an airfoil for a turbine engine includes an airfoil that has pressure and suction sides and extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve that corresponds to a relationship between a leading edge dihedral and a span position. The leading edge dihedral has a portion of the curve with a change in dihedral in the range of 90% to 100% span position of greater than 10&#xb0;. A positive dihedral corresponds to suction side-leaning. A negative dihedral corresponds to pressure side-leaning.

Gas turbine engine airfoil

Growing community of inventors

Glastonbury, CT, United States of America

Mani Sadeghi